Inertial particle separator for engine inlet

ABSTRACT

An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.

TECHNICAL FIELD

The application relates generally to aircraft engine inlets and, moreparticularly, to particle separation at such inlets.

BACKGROUND OF THE ART

Aircraft engines such as gas turbine engines may be susceptible toincrease wear and/or failures when some types of particles are ingestedin the engine inlets. Intake assemblies of turboshaft and turbopropengines typically include a particle separator to minimize ingestion ofparticles in the engine inlet.

Some particle separators rely on solid vanes and/or multiple curves orturns between the inlet duct and the bypass duct to create obstructionsto the flow allowing the particles to drop out of the airflow before theflow reaches the engine inlet. However, obstructions to the flow createpressure losses and/or flow distortions which are detrimental to engineperformances.

SUMMARY

In one aspect, there is provided an aircraft engine having an inertialparticle separator communicating with an engine inlet of the aircraftengine, the inertial particle separator comprising: an inlet ductdefining an intake communicating with an environment of the engine; anintermediate duct extending generally transversally from the inlet ductto the engine inlet, the intermediate duct communicating with the inletduct adjacent a downstream end of the inlet duct; and a bypass duct influid communication with and extending downstream from the inlet ductand intermediate duct, the bypass duct defining an outlet communicatingwith the environment of the engine; wherein a wall of the intermediateduct intersects a wall of the inlet duct on an engine side of the wallof the inlet duct, the engine side of the wall of the inlet ductdefining an engine-side inlet air flow line of the inertial particleseparator, a wall of the bypass duct intersecting the wall of theintermediate duct closer to a central axis of the engine than anextension of the engine-side inlet air flow line into the bypass duct.

In another aspect, there is provided a gas turbine engine comprising: atleast one rotatable shaft in driving engagement with a compressorsection and with a turbine section and defining a central axis of theengine; an engine inlet in fluid communication with the compressorsection; an inertial particle separator comprising: an inlet ductdefining an intake and including a wall having opposed engine and outersides, the engine side located between the central axis of the engineand the outer side; an intermediate duct extending radially inwardlyfrom the inlet duct to the engine inlet, the intermediate ductcommunicating with the inlet duct adjacent a downstream end of the inletduct, a wall of the intermediate duct intersecting the wall of the inletduct on the engine side; and a bypass duct in fluid communication withand extending downstream from the inlet duct and intermediate duct todefine an outlet; wherein in a plane containing central axes of theinlet duct and of the bypass duct, an imaginary straight line overlapsthe engine side of the wall of the inlet duct and extends downstreamfrom the inlet duct into the bypass duct; and wherein an intersectionbetween a wall of the bypass duct and the wall of the intermediate ductis located radially inwardly of the imaginary straight line.

In a further aspect, there is provided a method of separating particlesfrom a flow for an inlet of an engine, the method comprising: directinga first portion of the flow including air and particles through an inletduct and into a bypass duct away from the inlet of the engine withoutimpacting a wall of an intermediate duct, the intermediate ductextending generally transversally from the inlet duct to the inlet ofthe engine; and directing a second portion of the flow including airthrough the inlet duct and turning the second portion of the flow awayfrom the first portion and into the intermediate duct to flow the secondportion to the inlet of the engine.

DESCRIPTION OF THE DRAWINGS

Reference is now made to the accompanying figures in which:

FIG. 1 is a schematic cross-sectional view of a gas turbine engine;

FIG. 2a is a schematic cross-sectional view of an inertial particleseparator in accordance with a particular embodiment, which may be usedwith the gas turbine engine of FIG. 1;

FIG. 2b is a schematic cross-sectional view of an inlet duct of theinertial particle separator of FIG. 2a , taken along line B-B;

FIG. 3 is a schematic cross-sectional view of an inertial particleseparator in accordance with another particular embodiment, which may beused with the gas turbine engine of FIG. 1;

FIG. 4 is a schematic cross-sectional view of the inertial particleseparator of FIG. 3 during non-icing conditions; and

FIG. 5 is a schematic cross-sectional view of the inertial particleseparator of FIG. 3 during icing conditions.

DETAILED DESCRIPTION

FIG. 1 illustrates a gas turbine engine 10 of a type preferably providedfor use in subsonic flight, generally comprising in serial flowcommunication an engine inlet 12 through which ambient air is received,a compressor section 14 for pressurizing the air, a combustor 16 inwhich the compressed air is mixed with fuel and ignited for generatingan annular stream of hot combustion gases, and a turbine section 18 forextracting energy from the combustion gases.

The engine 10 includes at least one rotatable shaft defining a centralaxis 20 of the engine. In the embodiment shown, two co-axial andindependently rotatable shafts are provided: a low pressure or powershaft 22, and a high pressure shaft 24. The high pressure shaft 24 isdriven by a high pressure portion 18H of the turbine section 18, anddrives the compressor section 14. The low pressure shaft 22 is driven bya low pressure portion 18L of the turbine section 18 which is locateddownstream of the high pressure portion 18H, and drives an output shaft26 engaged to a propeller 28; the output shaft 26 is driven through areduction gearbox 30.

Although the engine 10 is shown as a turboprop engine, it is understoodthat the engine 10 may have any suitable alternate configuration,including, but not limited to, a turboshaft configuration. Moreover,although the engine 10 is shown as a gas turbine engine, it isunderstood that the engine may have any other suitable configuration.

Referring to FIGS. 2a-2b , an inertial particle separator 40 inaccordance with a particular embodiment is shown, configured forcommunicating with the engine inlet 12. The particle separator 40generally includes an inlet duct 42, an intermediate duct 44, and abypass duct 46.

The inlet duct 42 defines an intake 48 communicating with theenvironment of the engine 10. The inlet duct 42 has a wall having anengine side 42 a and an outer side 42 b radially spaced from oneanother, with the outer side 42 b being located radially outwardly ofthe engine side 42 a with respect to the central axis 20 of the engine10, i.e. the engine side 42 a is located between the central axis 20 ofthe engine 10 and the outer side 42 b. In a particular embodiment and ascan be seen in FIG. 2b , the inlet duct 42 has an arcuate cross-section,and the engine and outer sides 42 a, 42 b are each defined by wallportions having a concave cross-sectional shape with the concavity beingoriented radially inwardly. Opposed wall portions 42 c extend betweenthe engine and outer sides 42 a, 42 b of the wall. Other configurationsmay be possible. For example, the inlet duct 42 may have a circular oroval cross-section, in which case the engine and outer sides 42 a, 42 bof the wall may be connected to each other in a continuous manner.

Referring back to FIG. 2a , the intermediate duct 44 is in fluidcommunication with the inlet duct 42 adjacent its downstream end. Theintermediate duct 44 extends radially inwardly, generally transversallyto the inlet duct 42, and is connected to the engine inlet 12. Theintermediate duct 44 has a wall with axially spaced apart upstream anddownstream wall portions 44 u, 44 d. The wall of the intermediate duct44, more particularly the upstream wall portion 44 a, intersects thewall of the inlet duct 42 on the engine side 42 a at a firstintersection 50. In the embodiment shown and as will be further detailedbelow, the engine side 42 a of the wall of the inlet duct 42 is straightalong its longitudinal direction, and the upstream wall portion 44 u iscurved at the intersection with the engine side 42 a of the inlet ductwall; accordingly the first intersection 50 is defined at the beginningof the curved wall.

It the present specification, including claims, the terms “intersection”and related terms (e.g. “intersects”) are intended to encompass thepoint of attachment of walls manufactured separately and attachedtogether through any suitable type of attachment, as well a point oftransition (e.g., change of direction) between adjacent portions of amonolithic wall.

Still referring to FIG. 2a , the bypass duct 46 is in fluidcommunication with the inlet duct 42 and intermediate duct 44, andextends downstream from the inlet duct 42 and from the intermediate duct44. The bypass duct 46 has a wall having an outer side 46 b extendingfrom a downstream end of the outer side 42 b of the wall of the inletduct 42. The wall of the bypass duct 46 also has an engine side 46 aintersecting the wall of the intermediate duct 44, more particularly thedownstream wall portion 44 d, at a second intersection 52. The inletduct 42, intermediate duct 44 and bypass duct 46 thus communicate witheach other at 54, and together define an “inverted T” shape. The bypassduct 46 defines an outlet 56 communicating with the environment of theengine. In a particular embodiment, the inertial particle separator 40defines a bypass ratio of at least 2%; in a particular embodiment, thebypass ratio is at least 5%. Other values are possible, including valuesgreater than 0. The bypass ratio can for example be provided passivelyby the pressure difference across the duct, or via a blower or ejectorsystem (not shown).

The bypass duct 46 is in general alignment with the inlet duct 42. Forexample, in the embodiment shown, a central axis 58 of the inlet duct 42extends from the inlet duct 42 into the bypass duct 46 beforeintersecting the wall 46 a, 46 b of the bypass duct 46. Also, in theembodiment shown, the central axis 58 of the inlet duct 42 does notextend through the outer side 46 b of the wall of the bypass duct 46,and extends through the engine side 46 a of the wall of the bypass duct46 only after penetrating the bypass duct 46, i.e. the interior surfaceof the engine side 46 a of the wall of the bypass duct 46 is locatedbetween the inlet duct 42 and the outer surface of the engine side 46 aof the wall of the bypass duct 46 along the central axis 58 of the inletduct 42.

It can be seen in FIG. 2a that the engine side 42 a of the wall of theinlet duct 42 defines an engine-side inlet air flow line F of theinertial particle separator. The wall of the bypass duct 46 intersectsthe wall of the intermediate duct 44 closer to the engine than anextension 62 of the engine-side inlet air flow line F into the bypassduct 46, i.e. the intersection 52 between the engine side 46 a of thebypass duct wall and downstream wall portion 44 d is located closer tothe central axis 20 of the engine than the extension 62 of theengine-side inlet air flow line into the bypass duct 46. Theintersection 52 between the engine side 46 a of the wall of the bypassduct 46 and the wall of the intermediate duct 44 is thus locatedradially inwardly of the extension 62 of the engine-side inlet air flowline into the bypass duct 46.

In the embodiment shown, the engine-side inlet air flow line and itsextension can be drawn as an imaginary straight line 62 defining aprolongation of the engine side 42 a of the wall of the inlet duct 42 ina plane containing the central axis 58 of the inlet duct 42 and acentral axis 60 of the bypass duct 46 (i.e., the plane of FIG. 2a ). Theimaginary straight line 62 overlaps the engine side 42 a of the wall ofthe inlet duct 42 adjacent the first intersection 50, and extendsdownstream from the inlet duct 42 into the bypass duct 46. Theintersection 52 between the walls of the intermediate duct 44 and of thebypass duct 46 is located radially inwardly of this imaginary straightline 62, i.e. the second intersection 52 is located radially inwardly ofa prolongation of the engine side 42 a of the wall of the inlet duct 42.In the embodiment shown, the intersection 52 between the walls of theintermediate duct 44 and of the bypass duct 46, and the outer side 46 bof the wall of the bypass duct 46, are located on opposed sides of theimaginary straight line 62.

The second intersection 52 is located radially inwardly of the extension62 of the engine-side inlet air flow line (imaginary straight line 62defining the prolongation of the engine side 42 a of the wall of theinlet duct 42) by a radial distance y. In a particular embodiment, theflow directed in the inlet duct 42 (which may include particles) flowsinto the bypass duct 46 without impacting the downstream wall portion 44d of the intermediate duct, since the engine side 42 a of the wall ofthe inlet duct 42 directs the flow radially outwardly of theoutward-most portion of the downstream wall portion 44 d (i.e., of thesecond intersection 52). In a particular embodiment, the secondintersection 52 is located radially inwardly of the prolongation of theengine side 42 a of the wall of the inlet duct 42 a sufficient distanceto provide adequate particle separation without the need to add anobstruction to the flow, e.g. to prevent the particles from hitting thedownstream wall portion 44 d and being turned with the air flowcirculating from the inlet duct 42 into the intermediate duct 44.

In the embodiment shown, the upstream wall portion 44 d of theintermediate duct 44 has a curved portion 64 extending from the inletduct 42 (i.e. from the first intersection 50) and a straight portion 66extending from the curved portion 64. The curved portion 64 thus defineda curved transition between the intermediate duct 44 and the inlet duct42. The curved transition can be represented by a curved central axis68, which is defined as a mean curve corresponding to the average (i.e.mid-span) between the curved portion 64 and a virtual curve V smoothlyconnecting the outer side 42 b of the wall of the inlet duct and thedownstream wall portion 44 d of the intermediate duct 44. In aparticular embodiment, the particle separator is configured so as tocorrespond to

$\frac{y}{R_{m}} > {A\left( {{\sin\left( \alpha_{t} \right)} - 1} \right)}$where y is the radial distance between the imaginary straight line 62(extension of the engine-side inlet air flow line) and the intersection52 between the walls of the intermediate and bypass ducts 44, 46, R_(m)is a mean radius of the central axis 68 of the transition between theintermediate duct 44 and the inlet duct 42, α_(t) is the angle definedbetween the first intersection 50 and the straight portion 66 of theupstream wall 44 u, i.e. the bend angle defined by the curved portion64, and A is a constant greater than 0. In a particular embodiment, Ahas a value within a range extending from 0.2 to 5.

In the embodiment shown, the inlet duct 42 and the bypass duct 46 eachhave a straight central axis 58, 60, with the two axes 58, 60 extendingslightly angled from each other. The walls 42 a, 42 b, 46 a, 46 b of theinlet duct 42 and of the bypass duct 46 also extend in a straight manneralong their longitudinal direction, i.e. they appear as straight linesin the plane of FIG. 2a . Other configurations are also possible. Forexample, one or both of the central axes 58, 60 may be curved.

A height H_(i) of the inlet duct 42 can be defined at the firstintersection 50, and a height H_(b) of the bypass duct 46 can be definedat the second intersection 52. In the embodiment shown, the outer sides42 b, 46 b of the walls of the inlet duct 42 and of the bypass duct 46extend non-parallel to each other but are only slightly angled withrespect to each other, and the height H_(b) of the bypass duct 46 isgreater than the height H_(i) of the inlet duct 42. In a particularembodiment, the height H_(i) of the inlet duct 42 is approximately 6inches; other values may alternately be used.

A width X of an inlet of the intermediate duct 44 can be defined betweenthe first and second intersections 50, 52, i.e. from the intersection 50between the walls of the inlet and intermediate ducts 42, 44 to theintersection 52 between the walls of the intermediate and bypass ducts44, 46, along the imaginary straight line 62 of the prolongation of theengine side 42 a of the wall of the inlet duct 42 (extension of theengine-side inlet air flow line). In a particular embodiment, theparticle separator is configured so as to correspond to

${\frac{M_{1}^{0,6}}{X}*H_{i}} > B$where X is the width of the inlet of the intermediate duct 44, M₁ is theMach number of the airflow at a particular engine operating condition atthe intersection between the outer walls 42 b, 46 b of the inlet duct 42and of the bypass duct 46, e.g. at the slight bend indicated at (1) inFIG. 2a , H_(i) is the height of the inlet duct 42 and B is a constant.In a particular embodiment, B has a value within a range extending from0.12 to 0.5. In a particular embodiment, the value of M₁ is 0.2. Otheroperating conditions are also possible.

In use and in a particular embodiment, at least some of the particlesare separated from the flow by directing a first portion 76 of the flowincluding air and particles through the inlet duct 42 and into thebypass duct 46 without impacting the downstream wall portion 44 d of theintermediate duct 44. The particles 76 continue through the bypass duct46 and are ejected through the outlet 56. A second portion 78 of theflow including air is also directed through the inlet duct 42, but turnsaway from the first portion into the intermediate duct 44 to reach theinlet 12 of the engine. Because of the turn required to direct the flowinto the intermediate duct 44, the particles having inertia too great tofollow the turn continue into the bypass duct 46 and are accordinglyseparated from the air flowing to the inlet 12 of the engine.

Referring to FIGS. 3-5, an inertial particle separator 140 in accordancewith another particular embodiment is shown, where elements similar tothose of the particle separator 40 of FIGS. 2a-2b are identified by thesame reference numeral and will not be further described herein. Theparticle separator 140 of FIGS. 3-5 includes an angled vane 170 locatedin the inlet duct 42. The vane 170 extends non-perpendicularly from theengine side 42 a of the wall of the inlet duct 42 and has an edge 172spaced from the wall of the inlet duct 42. In a particular embodiment,the vane 170 has a fixed position within the inlet duct 42.

Referring particularly to FIG. 3, the vane 170 extends at an angle θfrom the engine side 42 a of the wall of the inlet duct 42, with theedge 172 being located downstream of the portion of the vane 170adjacent the engine side 42 a. The edge 172 is located at a radialdistance g from the outer side 42 b of the wall of the inlet duct 42,and at an axial distance d from a central axis 174 of the intermediateduct 44. The edge 172 is located radially outwardly of the intersection52 between the walls of the intermediate duct 44 and of the bypass duct46. In a particular embodiment, the angle θ has a value from 10° to 40°,the radial distance g (or gap) has a value from 15% to 40% of the heightH_(i) of the inlet duct 42, and the axial distance d has a value from40% to 60% of the width X of the inlet of the intermediate duct 44. Itis understood that other values are also possible, and that each ofthese values may be applicable independently of the others.

In the embodiment shown, the vane 170 is porous, with openingsconfigured so as to allow most particles to flow therethrough innon-icing conditions. The vane 170 is configured so as to reduce,minimize or avoid deflection of the flow during non-icing conditions;for example, the porous vane 170 allows for lower flow distortions and alower pressure loss than a similarly sized solid vane including louversto let the flow therethrough. The openings of the porous vane 170 arehowever sized such that in icing conditions, the porous vane 170 allowsto aggregate ice, i.e. the water droplets (e.g. super cooled waterdroplets) will form a coating of ice on the vane 170, blocking theopenings and causing the vane 170 to act as a solid vane.

In a particular embodiment, the vane 170 includes or is constituted by ascreen (e.g. mesh material), for example a screen defining openinghaving a cross-sectional dimension of about 1-2 millimetres. Otherdimensions are also possible. Alternately, the porous vane 170 can beconfigured as a perforated plate, or be defined in part or in whole byopen cell material such as honeycomb material. Other configurations arealso possible.

The particle separator 140 may also include an engine screen 180 orother suitable porous wall between the intermediate duct 44 and theengine inlet 12, or within the intermediate duct 44, for furtherfiltering of particles.

FIG. 4 shows the vane 170 under non-icing conditions. Larger particlesor large debris 176 (e.g. rain, sand, birds) enter the intake 48 andflow through the inlet duct 42. These particles 176 are separated fromthe engine flow by the bend at the intermediate duct 44 and directedinto the bypass duct 46 to be expelled through the outlet 56. The airflow, as well as the particles small enough, pass through the porousvane 170 with no or with minimal deflection. Part of the air flow 178turns into the intermediate duct 44 and reaches the engine inlet 12.

In a particular embodiment, the intersection 52 between the walls of thebypass duct 46 and of the intermediate duct 44 is located radiallyinwardly of the prolongation of the engine side 42 a of the wall of theinlet duct 42 by a distance y, as detailed above for the embodiment ofFIGS. 2a-2b . In a particular embodiment, such a configuration providesfor particle separation when the vane 170 defines no or minimalobstruction to the flow, i.e. in non-icing conditions.

FIG. 5 shows the vane 170 under icing conditions. Icing particle orother particles/debris enter the intake 48 and flow through the inletduct 42. Ice has accreted on the vane 170 to block its openings;accordingly the vane 170 acts as a solid wall and blocks a portion ofthe inlet duct 42. The flow of particles 176 and of air 178 isaccelerated through the area under the vane 170. The inertia of theparticles 176 (e.g. icing particles) is increased as they areaccelerated, separated from the engine flow, and directed into thebypass duct 46, unable to turn to reach the intermediate duct 44. Partof the air flow 178 turns into the intermediate duct 44 and reaches theengine inlet 12.

In use and in a particular embodiment, at least some of the particlesare separated from the flow by directing a first portion of the flowincluding air and particles 176, and a second portion of the flowincluding air 178, through the inlet duct 42. Part of both portions 176,178 of the flow goes through the porous vane 170 during non-icingconditions. During icing conditions, once the openings of the vane 170are blocked by an iced coating, the portions 176, 178 of the flow aredeflected by the vane 170 away from the intermediate duct 44. Theincreased turn required for the air 178 to reach the intermediate duct44 provides separation from the heavier water droplets, which continueinto the bypass duct 46 to be ejected through the outlet 56.

In a particular embodiment, the particle separator 40, 140 allows toprotect a turboprop/turboshaft engine against foreign object ingestionincluding water, icing particles, and large debris. In a particularembodiment, the particle separator 40, 140 allows for particleseparation to be performed with a relatively simple mechanicalarrangement with minimal additional weight on the inlet assembly.

The use of a porous vane 170 (e.g. including/constituted by a screen)allows for the vane 170 to have a fixed position while minimizing itsimpact on the flow during non-icing conditions. In contrast to solidvanes that are actuated to be moved out of the flow during non-icingconditions to minimize their impact on the flow, the particle separator140 with fixed porous vane 170 can provide for reduced pressure loss,complexity and/or weight.

Although the particle separator 40, 140 has been shown as configured fora forward facing intake of a reversed flow engine with a singleintermediate duct, it is understood that various alternateconfigurations are possible, including for a through flow engine, a sidefacing intake, a bifurcated intermediate duct and/or a bifurcated inletduct.

The above description is meant to be exemplary only, and one skilled inthe art will recognize that changes may be made to the embodimentsdescribed without departing from the scope of the invention disclosed.Modifications which fall within the scope of the present invention willbe apparent to those skilled in the art, in light of a review of thisdisclosure, and such modifications are intended to fall within theappended claims.

The invention claimed is:
 1. An aircraft engine having an inertialparticle separator communicating with an engine inlet of the aircraftengine, the inertial particle separator comprising: an inlet ductdefining an intake communicating with an environment of the engine; anintermediate duct extending generally transversally from the inlet ductto the engine inlet, the intermediate duct communicating with the inletduct adjacent a downstream end of the inlet duct; and a bypass duct influid communication with and extending downstream from the inlet ductand intermediate duct, the bypass duct defining an outlet communicatingwith the environment of the engine; wherein a wall of the intermediateduct intersects a wall of the inlet duct on an engine side of the wallof the inlet duct, the engine side of the wall of the inlet ductdefining an engine-side inlet air flow line of the inertial particleseparator, a wall of the bypass duct intersecting the wall of theintermediate duct closer to a central axis of the aircraft engine thanan extension of the engine-side inlet air flow line into the bypass ductwhile a central axis of the inlet duct extends from the inlet duct intothe bypass duct before intersecting an engine side of the wall of thebypass duct.
 2. The aircraft engine as defined in claim 1, wherein aheight of the inlet duct is defined adjacent the intermediate duct, aheight of the bypass duct is defined adjacent the intermediate duct, andthe height of the bypass duct is greater than the height of the inletduct.
 3. The aircraft engine as defined in claim 1, wherein central axesof the inlet duct and of the bypass duct are straight.
 4. The aircraftengine as defined in claim 1, wherein the wall of the intermediate ducthas a curved portion extending from the wall of the inlet duct and astraight portion extending from the curved portion, the curved portionextending along an angle αt, the curved portion defining a curvedcentral axis for a transition between the inlet and intermediate ducts,the curved central axis having a mean radius Rm, wherein a radialdistance y is defined between the intersection of the wall of the bypassduct with the wall of the intermediate duct and the extension of theengine-side inlet air flow line, and wherein${\frac{y}{R_{m}} > {A\left( {{\sin\left( \alpha_{t} \right)} - 1} \right)}},$where A is a constant greater than
 0. 5. The aircraft engine as definedin claim 4, wherein A has a value within a range extending from 0.2 to5.
 6. The aircraft engine as defined in claim 1, wherein the inertialparticle separator is configured for an engine operating conditiondefining an airflow with a Mach number M₁ at the downstream end of theinlet duct, wherein a width X of an inlet of the intermediate duct isdefined along the engine-side inlet air flow line, wherein the inletduct has a height H_(i), and wherein${{\frac{M_{1}^{0,6}}{X}*H_{i}} > B},$ where B is a constant having avalue within a range extending from 0.12 to 0.5.
 7. The aircraft engineas defined in claim 1, further comprising an angled vane extendingnon-perpendicularly from the engine side of the inlet duct to an edgespaced from the wall of the inlet duct.
 8. The inertial particleseparator as defined in claim 7, wherein the angled vane has a fixedposition and includes openings allowing particles to pass therethrough,the openings sized so as to aggregate ice and be blocked by an icecoating under icing conditions.
 9. A gas turbine engine comprising: atleast one rotatable shaft in driving engagement with a compressorsection and with a turbine section and defining a central axis of theengine; an engine inlet in fluid communication with the compressorsection; an inertial particle separator comprising: an inlet ductdefining an intake and including a wall having opposed engine and outersides, the engine side located between the central axis of the engineand the outer side; an intermediate duct extending radially inwardlyfrom the inlet duct to the engine inlet, the intermediate ductcommunicating with the inlet duct adjacent a downstream end of the inletduct, a wall of the intermediate duct intersecting the wall of the inletduct on the engine side; and a bypass duct in fluid communication withand extending downstream from the inlet duct and intermediate duct todefine an outlet; wherein in a plane containing central axes of theinlet duct and of the bypass duct, an imaginary straight line overlapsthe engine side of the wall of the inlet duct and extends downstreamfrom the inlet duct into the bypass duct; and wherein an intersectionbetween a wall of the bypass duct and the wall of the intermediate ductis located radially inwardly of the imaginary straight line relative tothe central axis of the engine while a central axis of the inlet ductextends from the inlet duct into the bypass duct before intersecting anengine side of the wall of the bypass duct.
 10. The gas turbine engineas defined in claim 9, wherein a height of the inlet duct is definedadjacent the intermediate duct, a height of the bypass duct is definedadjacent the intermediate duct, and the height of the bypass duct isgreater than the height of the inlet duct.
 11. The gas turbine engine asdefined in claim 9, wherein the central axes of the inlet duct and ofthe bypass duct are straight.
 12. The gas turbine engine as defined inclaim 9, wherein the wall of the intermediate duct has a curved portionextending from the wall of the inlet duct and a straight portionextending from the curved portion, the curved portion extending along anangle α_(t), the curved portion defining a curved central axis for atransition between the inlet and intermediate ducts, the curved centralaxis having a mean radius R_(m), wherein a radial distance y is definedbetween the intersection of the wall of the bypass duct with the wall ofthe intermediate duct and the imaginary straight line, and wherein${\frac{y}{R_{m}} > {A\left( {{\sin\left( \alpha_{t} \right)} - 1} \right)}},$where A is a constant greater than
 0. 13. The gas turbine engine asdefined in claim 12, wherein A has a value within a range extending from0.2 to
 5. 14. The gas turbine engine as defined in claim 9, wherein theinertial particle separator is configured for an engine operatingcondition defining an airflow with a Mach number M₁ at the downstreamend of the inlet duct, wherein a width X of an inlet of the intermediateduct is defined along the engine-side inlet air flow line, wherein theinlet duct has a height H_(i), and wherein${{\frac{M_{1}^{0,6}}{X}*H_{i}} > B},$ where B is a constant having avalue within a range extending from 0.12 to 0.5.
 15. The gas turbineengine as defined in claim 9, further comprising an angled vaneextending non-perpendicularly from the engine side of the wall of theinlet duct to an edge spaced from the wall of the inlet duct.
 16. Theinertial particle separator as defined in claim 15, wherein the angledvane has a fixed position and includes openings allowing particles topass therethrough, the openings sized so as to aggregate ice and beblocked by an ice coating under icing conditions.
 17. A method ofseparating particles from a flow for an inlet of an engine, the methodcomprising: directing a first portion of the flow including air andparticles through an inlet duct and into a bypass duct away from theinlet of the engine without impacting a wall of an intermediate duct,the intermediate duct extending generally transversally from the inletduct to the inlet of the engine, an intersection between the wall of theintermediate duct and a wall of the bypass duct located closer to acentral axis of the engine than an intersection between the wall of theintermediate duct and a wall of the inlet duct while a central axis ofthe inlet duct extends from the inlet duct into the bypass duct beforeintersecting an engine side of the wall of the bypass duct; anddirecting a second portion of the flow including air through the inletduct and turning the second portion of the flow away from the firstportion and into the intermediate duct to flow the second portion to theinlet of the engine.
 18. The method as defined in claim 17, furthercomprising: during non-icing conditions, flowing the first and secondportions of the flow at least in part through openings of a vaneextending within the inlet duct; and during icing conditions, uponblocking of the openings of the vane by an ice coating, deflecting thefirst and second portions of the flow within the inlet duct away fromthe intermediate duct with the vane.